Aircraft

Abstract

The utility model discloses an aircraft which comprises a rack and a control module, and the control module is fixedly connected with a power line. A wire passing through hole is formed in the rack, and a wire passing sleeve is fixedly connected in the wire passing through hole; the end, away from the control module, of the power line penetrates through the line passing sleeve and extends to the outer side of the rack, and the power line is fixedly connected with the line passing sleeve; the rack comprises a first rack face and a second rack face which are parallel, the wire passing through hole penetrates through the first rack face and the second rack face, and a power line located in the wire passing sleeve is perpendicular to the first rack face. The wire passing sleeve is arranged in the wire passing through hole, so that a power line connected with the control module does not directly contact with the rack when penetrating through the rack, but indirectly contacts with the rack through the wire passing sleeve, and the influence of the power line on the flight of the aircraft can be greatly reduced.

Description

Technical Field

[0001] This utility model relates to the field of unmanned driving, and in particular to an aircraft. Background Technology

[0002] Currently, aircraft typically use batteries installed on the aircraft to power it, allowing the aircraft to fly freely. However, the limited battery capacity restricts the flight time, and large-capacity batteries are difficult to use in aircraft due to their large size and weight.

[0003] Chinese patent application number 201420454806.3 discloses a ground-powered multirotor aircraft, including an aircraft body and a power supply that provides alternating current. The power supply is located on the ground, and a power line extends from the power supply; the other end of the power line is connected to a current-to-voltage converter on the aircraft body. This patent discloses a method of directly connecting the power line to the aircraft to supply power. However, in this method, the power line is prone to being at an angle to the aircraft during flight, thus affecting the aircraft's flight. Utility Model Content

[0004] The purpose of this invention is to provide an aircraft to solve the problem of the power cable affecting the aircraft when the power cable is connected to the aircraft.

[0005] To achieve this objective, the present invention adopts the following technical solution:

[0006] An aircraft includes a frame and a control module, wherein the control module is fixedly connected to a power cable;

[0007] The frame has through holes for wires, and a wire sleeve is fixedly connected in the through holes; the end of the power cord away from the control module passes through the wire sleeve and extends to the outside of the frame, and the power cord and the wire sleeve are fixedly connected.

[0008] The rack includes a first rack surface and a second rack surface that are parallel to each other. The through hole passes through the first rack surface and the second rack surface. The power cable located in the through sleeve is perpendicular to the first rack surface.

[0009] Optionally, the through-hole has a through-direction perpendicular to the first frame surface;

[0010] The cable guide sleeve has a hole for the power cable to pass through, and the power cable and the hole are interference-fitted; the cable guide sleeve includes a top surface and a bottom surface parallel to the first frame surface, the hole penetrates the top surface and the bottom surface, and the penetration direction of the hole is perpendicular to the top surface.

[0011] Optionally, the rack includes a rack base plate, the through hole is formed on the rack base plate, and the first rack surface and the second rack surface are two opposite surfaces of the rack base plate;

[0012] The distance between the first frame surface and the second frame surface is less than the distance between the top surface and the bottom surface of the sleeve. The middle part of the cable guide sleeve is located in the cable through hole and the two ends are located outside the cable through hole. The cable guide sleeve includes a sleeve side surface perpendicular to the top surface of the sleeve. A sleeve groove is formed around the sleeve side surface. When the cable guide sleeve is located in the cable through hole, the frame base plate around the cable through hole is engaged in the sleeve groove.

[0013] The middle part of the wire guide sleeve and the wire guide hole are interference-fitted, and the sleeve groove and the frame base plate are interference-fitted.

[0014] Optionally, the wire guide sleeve is made of an elastic material.

[0015] Optionally, the elastic material is rubber.

[0016] Optionally, the wire guide sleeve is a one-piece molded structure.

[0017] Optionally, the end of the power cord away from the control module may be detachably connected to a power source.

[0018] Optionally, the thickness of the sleeve groove is less than the thickness of the frame base plate.

[0019] Optionally, both the through hole and the sleeve hole are circular holes, and both the power cord and the sleeve are cylindrical; the middle part of the sleeve is the part between the bottom of the sleeve groove, and its diameter is larger than the diameter of the through hole; the diameter of the power cord is larger than the diameter of the sleeve hole.

[0020] Optionally, the top surface of the sleeve and the side surface of the sleeve are connected by an arc surface, and the bottom surface of the sleeve and the side surface of the sleeve are connected by an arc surface.

[0021] Optionally, the rack base plate is fixedly connected to a rack motherboard, and the rack motherboard is fixedly connected to a rack top plate;

[0022] The control module includes a flight controller and an electronic speed controller, with the flight controller fixedly connected to the frame base plate;

[0023] A single-point ranging module and multiple blade modules are fixedly connected to the mainboard of the frame. The blade module includes a motor.

[0024] The electronic speed controller is fixedly connected to the top plate of the frame, and a radar is also fixedly connected to the top plate of the frame;

[0025] The power cord is fixedly connected to the electronic speed controller, the electronic speed controller is electrically connected to the flight controller and the motor, and the flight controller is electrically connected to the single-point ranging module and the radar.

[0026] Optionally, the rack motherboard is located between the rack top plate and the rack bottom plate, and a plurality of first support columns are fixedly connected between the rack motherboard and the rack bottom plate, and a plurality of second support columns are fixedly connected between the rack motherboard and the rack top plate;

[0027] The flight controller is located between the main frame and the base plate of the frame, and multiple third support columns and multiple shock-absorbing balls are fixedly connected between the flight controller and the base plate of the frame;

[0028] The single-point ranging module includes a ranging base block, with a ranging protrusion formed by the center of the top surface of the ranging base block. A protrusion through-hole matching the shape of the ranging protrusion is provided on the main frame. The ranging base block is located between the bottom plate of the frame and the main frame. The ranging protrusion extends through the protrusion through-hole to the space between the main frame and the top plate of the frame. A ranging avoidance hole for avoiding laser emission from the ranging protrusion is provided on the top plate of the frame. A ranging support plate is fixedly connected to the main frame, and the ranging base block is located between the ranging support plate and the main frame and is clamped between them.

[0029] The rack motherboard is fixedly connected to multiple extension arms, and each of the multiple extension arms corresponds to a multiple of the blade modules. Each blade module is fixedly connected to the end of its corresponding extension arm that is away from the rack motherboard.

[0030] Optionally, the rack motherboard is fixedly connected to four extension arms. The rack motherboard is square, and the four extension arms are respectively fixed to the four corners of the rack motherboard. The four extension arms and the rack motherboard are on the same plane and are integrally formed.

[0031] The blade module also includes a blade protective cover and blades; the blade protective cover is fixedly connected to the extension arm, the motor and the blades are both located in the blade protective cover, the motor is fixedly connected to the blade protective cover, and the blades are fixedly connected to the output shaft of the motor;

[0032] The first, second, and third support columns are all nylon columns, while the main frame, top frame, and bottom frame are all carbon fiber.

[0033] Optionally, the blade protection cover includes a top of the protection cover, a bottom of the protection cover, and a plurality of protective cover baffles, wherein one end of each protective cover baffle is fixedly connected to the top of the protection cover, and the other end is fixedly connected to the bottom of the protection cover;

[0034] The protective cover bottom includes a circular bottom plate parallel to the main frame board. An inner ring plate is fixedly connected around the inner edge of the circular bottom plate, and an outer ring plate is fixedly connected around the outer edge of the circular bottom plate. Both the inner and outer ring plates are perpendicular to the circular bottom plate. The distance between the plane of the circular bottom plate and the main frame board is greater than the distance between the base plate of the frame and the main frame board support. When the aircraft is placed on the plane, the circular bottom plate contacts the plane.

[0035] The blade includes a central blade, which is fixedly connected to the output shaft of the motor. Multiple blades are fixedly connected to the central blade and are distributed at equal intervals around the central blade. Multiple protective cover baffles correspond one-to-one with the multiple blades, and there is a hollow space between two adjacent protective cover baffles.

[0036] The protective cover baffle includes a top baffle and a side baffle that are fixedly connected. The side of the top baffle away from the side baffle is fixedly connected to the side surface of the top of the protective cover, and the side baffle away from the top baffle is fixedly connected to the top surface of the inner ring piece. The top baffle and the side baffle are connected by an arc surface.

[0037] The top of the protective cover is parallel to the main board of the frame and is in the shape of a circular plate; the motor is fixedly connected to the bottom surface of the top of the protective cover; the top baffle is parallel to the top of the protective cover, and the side baffle and the inner ring plate form an acute angle.

[0038] The top baffle is parallel to the blade, and the projections of the top baffle and the side baffle on the plane where the blade is located overlap with the blade; the top baffle of the protective cover has a weight reduction hole, and the side baffle has a weight reduction hole; the blade protective cover is an integrally formed structure.

[0039] Compared with the prior art, the present invention has the following beneficial effects:

[0040] The aircraft provided by this utility model uses a cable guide sleeve installed in the cable guide hole to ensure that the power cable connected to the control module does not directly contact the frame when passing through it, but rather indirectly contacts the frame through the cable guide sleeve. The cable guide sleeve ensures that the portion of the power cable within the sleeve remains perpendicular to the frame; furthermore, it allows the weight of the power cable to act on the cable guide sleeve first before being transmitted to the frame, preventing the power cable from directly affecting the frame. This significantly reduces the impact of the power cable on the aircraft's flight. Attached Figure Description

[0041] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0042] The structures, proportions, sizes, etc., shown in the accompanying drawings of this specification are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed in the specification, and are not intended to limit the implementation conditions of this utility model. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size, without affecting the effects and purposes that this utility model can produce, should still fall within the scope of the technical content disclosed in this utility model.

[0043] Figure 1 A schematic diagram of the structure of the aircraft provided in the embodiment of this utility model;

[0044] Figure 2 This is a schematic diagram of the structure of the frame base plate provided in an embodiment of the present utility model;

[0045] Figure 3 A cross-sectional view of the wire guide sleeve provided in an embodiment of this utility model;

[0046] Figure 4 Another cross-sectional view of the wire guide sleeve provided in this embodiment of the utility model;

[0047] Figure 5 This is a schematic diagram of the structure of the wire guide sleeve provided in an embodiment of the present utility model;

[0048] Figure 6 Another structural schematic diagram of the aircraft provided in this embodiment of the utility model;

[0049] Figure 7 Another structural schematic diagram of the aircraft provided for an embodiment of this utility model;

[0050] Figure 8 A side view of the aircraft provided for an embodiment of this utility model;

[0051] Figure 9 This is a schematic diagram of the structure of the propeller module provided in an embodiment of the present utility model.

[0052] Illustrations: 1. Frame; 10. Cable guide hole; 11. Frame base plate; 12. Frame mainboard; 13. Frame top plate; 14. Extension arm; 15. Shock absorber ball; 2. Cable guide sleeve; 201. Top surface of the sleeve; 202. Bottom surface of the sleeve; 203. Side surface of the sleeve; 21. Sleeve hole; 22. Sleeve groove; 3. Power cable; 41. Flight controller; 42. Electronic speed controller; 43. Radar; 44. Single-point ranging module; 441 1. Distance measuring base block; 442. Distance measuring protrusion; 45. Distance measuring support plate; 5. Propeller module; 51. Motor; 52. Propeller blade; 521. Center propeller; 522. Blade; 53. Propeller blade protective cover; 531. Protective cover top; 532. Protective cover bottom; 5321. Circular bottom plate; 5322. Inner ring plate; 5323. Outer ring plate; 533. Protective cover baffle; 5331. Top baffle; 5332. Side baffle. Detailed Implementation

[0053] To make the utility model's objectives, features, and advantages more apparent and understandable, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described below are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present utility model.

[0054] In the description of this utility model, it should be understood that the terms "upper," "lower," "top," "bottom," "inner," "outer," "front," "rear," "left," and "right," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. It should be noted that when a component is considered to be "connected / set" to another component, it can be connected / set to another component, or it may simultaneously have a component centrally positioned.

[0055] The technical solution of this utility model will be further described below with reference to the accompanying drawings and specific embodiments.

[0056] Please refer to Figure 1-2 This utility model provides an aircraft, including a frame 1 and a control module, with a power cable 3 fixedly connected to the control module.

[0057] A wire-passing hole 10 is provided on the frame 1, and a wire-passing sleeve 2 is fixedly connected in the wire-passing hole 10. The end of the power cord 3 away from the control module passes through the wire-passing sleeve 2 and extends to the outside of the frame 1. The power cord 3 and the wire-passing sleeve 2 are fixedly connected.

[0058] The rack 1 includes a first rack surface and a second rack surface that are parallel to each other. The through hole 10 passes through the first rack surface and the second rack surface. The power cable 3 located in the through sleeve 2 is perpendicular to the first rack surface.

[0059] In the aircraft provided in this embodiment, the power cable 3 does not directly contact the frame 1 when passing through it, but indirectly contacts the frame 1 through the cable guide sleeve 2. The cable guide sleeve 2 ensures that the portion of the power cable 3 within the cable guide sleeve 2 remains perpendicular to the frame 1; on the other hand, it allows the weight of the power cable 3 to act on the cable guide sleeve 2 first before being transmitted to the frame 1, preventing the power cable 3 from directly affecting the frame 1. This greatly reduces the impact of the power cable 3 on the flight of the aircraft.

[0060] Please refer to Figure 1-5 The through-hole 10 is perpendicular to the first frame surface. The cable sleeve 2 has a sleeve hole 21 for the power cable 3 to pass through. The power cable 3 and the sleeve hole 21 are interference-fitted, so the power cable 3 is fixed in the sleeve hole 21 and cannot slide or rotate within it. The cable sleeve 2 includes a top surface 201 and a bottom surface 202 parallel to the first frame surface. The sleeve hole 21 penetrates both the top surface 201 and the bottom surface 202, and its through-hole direction is perpendicular to the top surface 201.

[0061] Specifically, the rack 1 includes a rack base plate 11, and through holes 10 are formed on the rack base plate 11. The first rack surface and the second rack surface are two opposite surfaces of the rack base plate 11.

[0062] The thickness of the frame base plate 11 is less than the thickness of the cable guide sleeve 2. The thickness of the frame base plate 11 is equal to the distance between the first frame surface and the second frame surface, and the thickness of the cable guide sleeve 2 is equal to the distance between the top surface 201 and the bottom surface 202 of the sleeve. Therefore, the cable guide sleeve 2 cannot be entirely located within the cable through hole 10; only the middle portion of the cable guide sleeve 2 is located within the cable through hole 10, while both ends are located outside the cable through hole 10.

[0063] The cable guide sleeve 2 includes a sleeve side surface 203 perpendicular to the top surface 201 of the sleeve. A sleeve groove 22 is provided around the sleeve side surface 203. When the cable guide sleeve 2 is located in the cable through hole 10, the frame base plate 11 around the cable through hole 10 is engaged in the sleeve groove 22.

[0064] The middle part of the cable guide sleeve 2 is interference-fitted with the cable through hole 10, and the sleeve groove 22 is interference-fitted with the frame base plate 11. This ensures a very stable fixation between the cable guide sleeve 2 and the frame base plate 11. Specifically, both the cable through hole 10 and the sleeve hole 21 are circular holes, and both the power cable 3 and the cable guide sleeve 2 are cylindrical. The middle part of the cable guide sleeve 2 is the portion between the bottom of the sleeve groove 22. Figure 4 (B) Its diameter is larger than the diameter of the through hole 10. The diameter of the power line 3 is larger than the diameter of the sleeve hole 21. The thickness of the sleeve groove 22 ( Figure 4 A) is less than the thickness of the frame base plate 11.

[0065] The cable guide sleeve 2 is made of an elastic material, preferably rubber. This allows the cable guide sleeve 2 to undergo elastic deformation when the power cable 3 is subjected to gravity, thus offsetting part of the force exerted by the power cable 3 and further reducing the impact of the power cable 3 on the aircraft's flight. The cable guide sleeve 2 is a one-piece molded structure.

[0066] The wire guide sleeve 2 can be elastically deformed. Therefore, even if the diameter of its two ends is larger than the diameter of the wire through hole 10, it can be elastically deformed to first insert into the wire through hole 10 and then extend out of the wire through hole 10 and return to its original shape. Through this process, the wire guide sleeve 2 can be installed on the frame base plate 11.

[0067] The top surface 201 and the side surface 203 of the sleeve are connected by an arc surface, and the bottom surface 202 and the side surface 203 of the sleeve are also connected by an arc surface. In this way, on the one hand, the cable guide sleeve 2 is more aesthetically pleasing, and on the other hand, when the cable guide sleeve 2 is installed on the frame base plate 11, the arc shape makes it easier for the cable guide sleeve 2 to be inserted into the cable through hole 10.

[0068] The end of the power cord 3 away from the control module can be detachably connected to a power source, which can be a fixed power source or a mobile power source, depending on the requirements.

[0069] Please refer to Figure 6-9 The frame base plate 11 is fixedly connected to the frame mainboard 12, and the frame mainboard 12 is fixedly connected to the frame top plate 13. The control module includes a flight controller 41 and an electronic speed controller 42. The flight controller 41 is fixedly connected to the frame base plate 11. A single-point ranging module 44 and multiple propeller blade modules 52 are fixedly connected to the frame mainboard 12. Each propeller blade module 52 includes a motor 51, and the output shaft of the motor 51 is fixedly connected to the propeller blades 52. The electronic speed controller 42 is fixedly connected to the frame top plate 13, and a radar 43 is also fixedly connected to the frame top plate 13. The electronic speed controller 42 is electrically connected to the flight controller 41 and the motors 51, and the flight controller 41 is electrically connected to the single-point ranging module 44 and the radar 43.

[0070] Specifically, the end of the power cord 3 furthest from the power source is fixedly connected to the electronic speed controller 42. Both ends of the power cord 3 between the electronic speed controller 42 and the cable sleeve 2 are fixedly connected to the frame 1, and the entire section of the power cord 3 is mounted on the frame 1, so it will not affect the aircraft during flight.

[0071] The flight controller 41 transmits relevant control signals to the electronic speed controller 42. The electronic speed controller 42 controls the speed and direction of rotation of the motor 51 according to the received control signals. The rotation of the motor 51 drives the propeller 52 to rotate, thereby providing power to the aircraft. The single-point ranging module 44 and the radar 43 can scan the surrounding environment and feed the environmental data back to the flight controller 41. The flight controller 41 adjusts the aircraft's attitude, speed, altitude, and other parameters in real time according to the environmental data to ensure stable flight in complex environments.

[0072] Specifically, the rack motherboard 12 is located between the rack top plate 13 and the rack bottom plate 11. Multiple first support columns are fixedly connected between the rack motherboard 12 and the rack bottom plate 11, and multiple second support columns are fixedly connected between the rack motherboard 12 and the rack top plate 13.

[0073] The flight controller 41 is located between the main board 12 and the base plate 11. Multiple third support columns are fixedly connected between the flight controller 41 and the base plate 11. Multiple shock-absorbing balls are also fixedly connected between the flight controller 41 and the base plate 11. The shock-absorbing balls can reduce the vibration of the flight controller 41 and prevent the flight of the aircraft from affecting the operation of the flight controller 41.

[0074] The single-point ranging module 44 includes a ranging base block 441. The center of the top surface of the ranging base block 441 protrudes to form a ranging protrusion 442. The main board 12 of the rack has a protrusion through hole that matches the shape of the ranging protrusion 442. The ranging base block 441 is located between the rack base plate 11 and the rack main board 12. The ranging protrusion 442 extends through the protrusion through hole to the area between the rack main board 12 and the rack top plate. The rack top plate has a ranging avoidance hole for avoiding the laser emitted by the ranging protrusion 442. The frame mainboard 12 is fixedly connected to a ranging support plate 45. The ranging base block 441 is located between the ranging support plate 45 and the frame mainboard 12 and is clamped by the ranging support plate 45 and the frame mainboard 12. The ranging support plate 45 and the frame mainboard 12 limit the vertical movement of the ranging base block 441. The ranging protrusion 442 is located in the protrusion through hole and is limited by the protrusion through hole in the forward, backward, left and right directions. Therefore, the single-point ranging module and the frame are firmly fixedly connected. By supporting the ranging base block 441 with the ranging support plate 45, there is no need to drill holes in the single-point ranging module 44, which is suitable for various single-point ranging modules 44 without hole fixing. In addition, the single-point ranging module 44 can be partially located between the frame mainboard 12 and the frame base plate 11, and partially located between the frame top plate and the frame mainboard 12. This allows the distance between the frame top plate and the frame mainboard 12 to be closer, making the overall aircraft more compact.

[0075] Radar 43 is mounted on the top plate 13 of the frame, so there are no supporting columns or other components around radar 43 that would affect its ability to emit lasers around the frame.

[0076] The mainboard 12 is fixedly connected to multiple extension arms 14, and each extension arm 14 corresponds to a multiple propeller 52 module. The propeller 52 module is fixedly connected to the end of its corresponding extension arm 14 away from the mainboard 12. Preferably, the aircraft provided in this embodiment is a quadcopter, that is, the mainboard 12 is fixedly connected to four extension arms 14. The mainboard 12 is square, and the four extension arms 14 are respectively fixed to the four corners of the mainboard 12. The four extension arms 14 and the mainboard 12 are on the same plane and are integrally formed.

[0077] The frame mainboard 12, frame top plate 13, and frame bottom plate 11 can be provided with weight reduction holes as needed. The first support column, the second support column, and the third support column are made of nylon, while the frame mainboard 12, frame top plate 13, and frame bottom plate 11 are made of carbon fiber. This ensures strong support and load-bearing capacity while also making the overall weight of the aircraft light.

[0078] In this embodiment, the blade 52 module further includes a blade protection cover 53 and blades 52. The blade protection cover 53 is fixedly connected to the extension arm 14, and both the motor 51 and the blades 52 are located within the blade protection cover 53. The motor 51 is fixedly connected to the blade protection cover 53, and the blades 52 are fixedly connected to the output shaft of the motor 51. The motor 51 is preferably a brushless motor 51.

[0079] Specifically, the blade protection cover 53 can be an integrally formed structure, including a top 531, a bottom 532, and multiple protective cover baffles 533. One end of each protective cover baffle 533 is fixedly connected to the top 531, and the other end is fixedly connected to the bottom 532.

[0080] The protective cover base 532 includes a circular base plate 5321 parallel to the main board 12 of the frame. An inner ring plate 5322 is fixedly connected around the inner edge of the circular base plate 5321, and an outer ring plate 5323 is fixedly connected around the outer edge of the circular base plate 5321. Both the inner ring plate 5322 and the outer ring plate 5323 are perpendicular to the circular base plate 5321. The distance between the plane of the circular base plate 5321 and the main board 12 of the frame is greater than the distance between the frame base plate 11 and the support of the main board 12 of the frame. When the aircraft is placed on the plane, the circular base plate 5321 contacts the plane.

[0081] The blade 52 includes a central blade 521, which is fixedly connected to the output shaft of the motor 51. Multiple blades 522 are fixedly connected to the central blade 521 and are distributed at equal intervals around the central blade 521. Multiple protective cover baffles 533 correspond one-to-one with the multiple blades 522, and there is a hollow space between two adjacent protective cover baffles 533.

[0082] The protective cover baffle 533 includes a top baffle 5331 and a side baffle 5332 that are fixedly connected. The side of the top baffle 5331 away from the side baffle 5332 is fixedly connected to the side surface of the top of the protective cover 531. The side baffle 5332 away from the top baffle 5331 is fixedly connected to the top surface of the inner ring piece 5322. The top baffle 5331 and the side baffle 5332 are connected by an arc surface.

[0083] The top of the protective cover 531 is parallel to the main board 12 of the frame and is in the shape of a circular plate. The motor 51 is fixedly connected to the bottom surface of the top of the protective cover 531. The top baffle 5331 is parallel to the top of the protective cover 531, and the side baffle 5332 and the inner ring plate 5322 form an acute angle.

[0084] The top baffle 5331 is parallel to the blade 522, and the projections of both the top baffle 5331 and the side baffle 5332 onto the plane containing the blade 522 overlap with the blade 522. The top baffle 5331 of the protective cover has a weight reduction hole, and the side baffle 5332 has a weight reduction hole.

[0085] The blade protector 53 not only protects the blade 52 from being damaged by surrounding obstacles during high-speed rotation of the blade 52, but also protects personnel from injury caused by the blade 52 due to the danger of high-speed rotation of the blade 52.

[0086] In this embodiment, when the aircraft is in flight, the direction facing the ground is taken as the bottom direction, and the direction facing the sky is taken as the top direction.

[0087] The aircraft provided in this embodiment has the following advantages:

[0088] 1. A cable sleeve 2 is installed at the cable through hole 10. When the power cable 3 passes through the rack 1, it does not directly contact the rack 1, but indirectly contacts the rack 1 through the cable sleeve 2. The cable sleeve 2 can keep the part of the power cable 3 in the cable sleeve 2 perpendicular to the rack 1; on the other hand, it can allow the weight of the power cable 3 to act on the cable sleeve 2 first and then be transmitted to the rack 1.

[0089] 2. The cable sleeve 2 is made of rubber. When the power cord 3 is subjected to gravity, the cable sleeve 2 can undergo elastic deformation to offset part of the force exerted by the power cord 3.

[0090] 3. The blade 52 is provided with a blade protection cover 53. The blade protection cover 53 not only protects the blade 52, but also supports the aircraft when it is not flying.

[0091] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. An aircraft, characterized in that, It includes a frame and a control module, wherein the control module is fixedly connected to a power cord; The frame has through holes for wires, and a wire sleeve is fixedly connected in the through holes; the end of the power cord away from the control module passes through the wire sleeve and extends to the outside of the frame, and the power cord and the wire sleeve are fixedly connected. The rack includes a first rack surface and a second rack surface that are parallel to each other. The through hole passes through the first rack surface and the second rack surface. The power cable located in the through sleeve is perpendicular to the first rack surface.

2. The aircraft according to claim 1, characterized in that, The through-hole is perpendicular to the first frame surface; The cable guide sleeve has a hole for the power cable to pass through, and the power cable and the hole are interference-fitted; the cable guide sleeve includes a top surface and a bottom surface parallel to the first frame surface, the hole penetrates the top surface and the bottom surface, and the penetration direction of the hole is perpendicular to the top surface.

3. The aircraft according to claim 2, characterized in that, The frame includes a frame base plate, the through hole is formed on the frame base plate, and the first frame surface and the second frame surface are two opposite surfaces of the frame base plate; The distance between the first frame surface and the second frame surface is less than the distance between the top surface and the bottom surface of the sleeve. The middle part of the cable guide sleeve is located in the cable through hole and the two ends are located outside the cable through hole. The cable guide sleeve includes a sleeve side surface perpendicular to the top surface of the sleeve. A sleeve groove is formed around the sleeve side surface. When the cable guide sleeve is located in the cable through hole, the frame base plate around the cable through hole is engaged in the sleeve groove. The middle part of the wire guide sleeve and the wire guide hole are interference-fitted, and the sleeve groove and the frame base plate are interference-fitted.

4. The aircraft according to claim 3, characterized in that, The thread guide sleeve is made of elastic material.

5. The aircraft according to claim 4, characterized in that, The elastic material is rubber, and the cable guide sleeve is an integrally molded structure; the end of the power cord away from the control module is detachably connected to a power source.

6. The aircraft according to claim 3, characterized in that, The thickness of the sleeve groove is less than the thickness of the frame base plate; Both the through hole and the sleeve hole are circular holes, and both the power cord and the through sleeve are cylindrical; the middle part of the through sleeve is the part between the bottom of the sleeve groove, and its diameter is larger than the diameter of the through hole; the diameter of the power cord is larger than the diameter of the sleeve hole. The top surface and the side surface of the sleeve are connected by an arc surface, and the bottom surface and the side surface of the sleeve are connected by an arc surface.

7. The aircraft according to claim 3, characterized in that, The rack base plate is fixedly connected to the rack motherboard, and the rack motherboard is fixedly connected to the rack top plate; The control module includes a flight controller and an electronic speed controller, with the flight controller fixedly connected to the frame base plate; A single-point ranging module and multiple blade modules are fixedly connected to the mainboard of the frame. The blade module includes a motor. The electronic speed controller is fixedly connected to the top plate of the frame, and a radar is also fixedly connected to the top plate of the frame; The power cord is fixedly connected to the electronic speed controller, the electronic speed controller is electrically connected to the flight controller and the motor, and the flight controller is electrically connected to the single-point ranging module and the radar.

8. The aircraft according to claim 7, characterized in that, The rack motherboard is located between the rack top plate and the rack bottom plate. A plurality of first support columns are fixedly connected between the rack motherboard and the rack bottom plate, and a plurality of second support columns are fixedly connected between the rack motherboard and the rack top plate. The flight controller is located between the main frame and the base plate of the frame, and multiple third support columns and multiple shock-absorbing balls are fixedly connected between the flight controller and the base plate of the frame; The single-point ranging module includes a ranging base block, with a ranging protrusion formed by the center of the top surface of the ranging base block. A protrusion through-hole matching the shape of the ranging protrusion is provided on the main frame. The ranging base block is located between the bottom plate of the frame and the main frame. The ranging protrusion extends through the protrusion through-hole to the space between the main frame and the top plate of the frame. A ranging avoidance hole for avoiding laser emission from the ranging protrusion is provided on the top plate of the frame. A ranging support plate is fixedly connected to the main frame, and the ranging base block is located between the ranging support plate and the main frame and is clamped between them. The rack motherboard is fixedly connected to multiple extension arms, and each of the multiple extension arms corresponds to a multiple of the blade modules. Each blade module is fixedly connected to the end of its corresponding extension arm that is away from the rack motherboard.

9. The aircraft according to claim 8, characterized in that, The rack motherboard is fixedly connected to four extension arms. The rack motherboard is square, and the four extension arms are respectively fixed to the four corners of the rack motherboard. The four extension arms and the rack motherboard are on the same plane and are integrally formed. The blade module also includes a blade protective cover and blades; the blade protective cover is fixedly connected to the extension arm, the motor and the blades are both located in the blade protective cover, the motor is fixedly connected to the blade protective cover, and the blades are fixedly connected to the output shaft of the motor; The first, second, and third support columns are all nylon columns, while the main frame, top frame, and bottom frame are all carbon fiber.

10. The aircraft according to claim 8, characterized in that, The blade protection cover includes a top cover, a bottom cover, and multiple protective cover baffles. One end of each protective cover baffle is fixedly connected to the top cover, and the other end is fixedly connected to the bottom cover. The protective cover bottom includes a circular bottom plate parallel to the main frame board. An inner ring plate is fixedly connected around the inner edge of the circular bottom plate, and an outer ring plate is fixedly connected around the outer edge of the circular bottom plate. Both the inner and outer ring plates are perpendicular to the circular bottom plate. The distance between the plane of the circular bottom plate and the main frame board is greater than the distance between the base plate of the frame and the main frame board support. When the aircraft is placed on the plane, the circular bottom plate contacts the plane. The blade includes a central blade, which is fixedly connected to the output shaft of the motor. Multiple blades are fixedly connected to the central blade and are distributed at equal intervals around the central blade. Multiple protective cover baffles correspond one-to-one with the multiple blades, and there is a hollow space between two adjacent protective cover baffles. The protective cover baffle includes a top baffle and a side baffle that are fixedly connected. The side of the top baffle away from the side baffle is fixedly connected to the side surface of the top of the protective cover, and the side baffle away from the top baffle is fixedly connected to the top surface of the inner ring piece. The top baffle and the side baffle are connected by an arc surface. The top of the protective cover is parallel to the main board of the frame and is in the shape of a circular plate; the motor is fixedly connected to the bottom surface of the top of the protective cover; the top baffle is parallel to the top of the protective cover, and the side baffle and the inner ring plate form an acute angle. The top baffle is parallel to the blade, and the projections of the top baffle and the side baffle on the plane where the blade is located overlap with the blade; the top baffle of the protective cover has a weight reduction hole, and the side baffle has a weight reduction hole. The blade protective cover is a one-piece molded structure.

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